53028 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Proposed Rules 

(C) Record measurement M1 indicated on 

the caliper gage on the component history 

card or equivalent record. 

(ii) On the tail rotor hub (TRH) side: 

(A) Remove the fairing and perform a 

measurement ‘‘M2’’ using a caliper gage 

between the flat face of the center plate (item 

c in the photograph in the Accomplishment 

Instructions under paragraph 3.B.4.b.(2) of 

ASB AS365–05.00.61, SA336–05.41, or 

EC155–05A022) and the face of the inner web 

(item ad in the photograph in the 

Accomplishment Instructions under 

paragraph 3.B.4.b.(2) of ASB AS365– 

05.00.61, SA336–05.41, or EC155–05A022) of 

the rotor hub on which the inner bearings of 

the TRH blades are installed. Position the 

caliper gage flat across the opening of the 

pitch change spider on R2 and R3 as shown 

in the right photograph in the 

Accomplishment Instructions under 

paragraph 3.B.4.b.(2) of ASB AS365– 

05.00.61, SA336–05.41, or EC155–05A022. 

(B) Record measurement M2 indicated on 

the caliper gage on the component history 

card or equivalent record. 

(C) Calculate a measurement ‘‘M3’’ by 

adding measurements M1 and M2. 

(D) Calculate the difference between 

measurement ‘‘M0’’ indicated on the TGB 

component history card or equivalent record 

and M3. 

(1) If the difference between measurement 

M0 and M3 is less than 0.5 mm (0.02 inch), 

perform an additional inspection for play in 

the bearing of the TGB control shaft and rod 

assembly by following the Accomplishment 

Instructions, paragraph 3.B.6., of ASB 

AS365–05.00.61, SA366–05.41, or EC155– 

05A022. If there is no axial play at the TRH 

pitch change spider, record value M3 on the 

component history card or equivalent record. 

If there is axial play at the TRH pitch change 

spider, replace the bearing with an airworthy 

bearing and perform a new reference 

measurement by following the requirements 

of paragraph (f)(6) of this AD. 

(2) If the difference between the 

measurements is equal to or greater than 0.5 

mm (0.02 inch), replace the bearing with an 

airworthy bearing and perform a new 

reference measurement by following the 

requirements of paragraph (f)(6) of this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Wilbanks, 

Aviation Safety Engineer, Rotorcraft 

Certification Office, Rotorcraft Directorate, 

FAA, 10101 Hillwood Pkwy, Fort Worth, 

Texas 76177; telephone (817) 222–5110; 

email 9-ASW-FTW-AMOC-Requests@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2012–0170R2, dated June 20, 2014. You 

may view the EASA AD on the internet at 

http://www.regulations.gov in Docket No. 

FAA–2015–3657. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6520 Tail Rotor Gearbox. 

Issued in Fort Worth, Texas, on August 21, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–21689 Filed 9–1–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3659; Directorate 

Identifier 2014–SW–050–AD] 

RIN 2120–AA64 

Airworthiness Directives; MD 

Helicopters Inc., Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for MD 

Helicopters Inc. (MDHI) Model 369A, 

369D, 369E, 369FF, 369HE, 369HM, 

369HS, 500N, and 600N helicopters 

with a certain part-numbered main rotor 

blade attach pin (pin) installed. This 

proposed AD would require ensuring 

the life limit of the pin as listed in the 

Airworthiness Limitations section of 

aircraft maintenance records and 

Instructions for Continued 

Airworthiness (ICA). If the hours timein-service (TIS) of a pin is unknown, or 

if a pin has exceeded its life limit, this 

proposed AD would require removing 

the affected pin from service. This 

proposed AD is prompted by a report 

from an operator who purchased pins 

that did not have life limit 

documentation. The proposed actions 

are intended to document the life limit 

to prevent a pin remaining in service 

beyond its fatigue life, which could 

result in failure of a pin, failure of a 

main rotor blade, and subsequent loss of 

control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by November 2, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

For service information identified in 

this proposed AD, contact Aerometals, 

3920 Sandstone Dr., El Dorado Hills, CA 

95762, telephone (916) 939–6888, fax 

(916) 939–6555, www.aerometals.aero. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy, Room 6N–321, 

Fort Worth, TX 76177. 

FOR FURTHER INFORMATION CONTACT: 

Galib Abumeri, Aviation Safety 

Engineer, Los Angeles Aircraft 

Certification Office, Transport Airplane 

Directorate, FAA, 3960 Paramount 

Blvd., Lakewood, California 90712; 

telephone (562) 627–5324; email 

Galib.Abumeri@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Proposed Rules 53029 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

We propose to adopt a new AD for 

MDHI Model 369A, 369D, 369E, 369FF, 

369HE, 369HM, 369HS, 500N, and 600N 

helicopters with a pin part-number (P/ 

N) 369X1004–5 installed. This proposed 

AD would require determining the 

number of hours TIS of each pin and 

whether the aircraft maintenance 

records contain a pin life limit. If the 

hours TIS are unknown, this proposed 

AD would require removing the pin 

from service. If the aircraft maintenance 

records do not contain a pin life limit, 

this proposed AD would require 

revising the records and establishing a 

life limit of 5,760 hours if the pin is 

installed on a Model 369A, 369HE, 

369HM, or 369HS helicopter, or 7,600 

hours if the pin is installed on a Model 

369D, 369E, 369FF, 500N, or 600N 

helicopter. This proposed AD would 

also require revising the records to add 

a statement that if a pin is interchanged 

between different model helicopters, 

then its life limit must be restricted to 

the lower life limit even if it was 

originally installed on a helicopter 

model with a higher life limit. Lastly, 

this proposed AD would prohibit 

installing a pin on any helicopter before 

these proposed requirements have been 

accomplished. 

Aerometals produces pin P/N 

369X1004–5 under a parts manufacturer 

approval as a replacement pin for MDHI 

P/N 369A1004–5. This proposed AD is 

prompted by a report from an operator 

who purchased Aerometals’ pins P/N 

369X1004–5 without life limit 

documentation. The FAA inadvertently 

approved the pins without a life limit in 

the Airworthiness Limitations section 

and without a restriction for parts that 

are interchanged between models with 

different life limits. A total of 5,133 

affected pins were sold by Aerometals 

without any indication that the parts 

were life-limited. The proposed actions 

are intended to correct the failure of 

these parts to have a documented life 

limit to prevent a pin remaining in 

service beyond its fatigue life, which 

could result in failure of a pin, failure 

of a main rotor blade, and subsequent 

loss of control of the helicopter. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all known relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of 

these same type designs. 

Related Service Information 

Aerometals has issued Aero-ICA–1001 

Supplemental Instructions for 

Continued Airworthiness, Revision NC, 

dated May 22, 2014, and Service 

Bulletin Aero-SB–1103, dated July 2, 

2014. The service bulletin specifies 

determining whether the helicopter has 

pins P/N 369X1004–5 installed and then 

reviewing the aircraft maintenance 

records to determine if the pins have a 

life limit identified. If the life limit is 

not the same as that listed in the ICA, 

the service bulletin specifies revising 

the life limit in the maintenance 

records. The service bulletin states that 

the pins were approved by the FAA as 

Parts Manufacturer Approval direct 

replacement parts with the same life 

limits as the parts they replace. 

However, they were sold without an 

FAA-approved supplemental ICA 

containing an Airworthiness Limitations 

Section specifically assigning these life 

limits to the pins. 

Proposed AD Requirements 

This proposed AD would require, 

within 100 hours TIS or during the next 

annual inspection, whichever comes 

first: 

° Reviewing the maintenance records 

and determining the hours TIS of each 

pin and whether there is a pin life limit 

listed in the Airworthiness Limitations 

Section of the applicable maintenance 

manual or ICA. If the hours TIS on a pin 

are unknown, the proposed AD would 

require removing the pin from service. 

° For Model 369A, 369HE, 369HM, 

and 369HS helicopters, if there is no pin 

life limit, establishing a new life limit of 

5,760 hours TIS and removing any pin 

from service that has 5,760 or more 

hours TIS. 

° For Model 369D, 369E, 369FF, 500N 

and 600N helicopters, if there is no pin 

life limit, establishing a new life limit of 

7,600 hours TIS and removing any pin 

from service that has 7,600 or more 

hours TIS. 

° For all model helicopters, 

establishing a requirement that if a pin 

is interchanged between model 

helicopters with different life limits, the 

life limit of the pin must be restricted 

to the lowest life limit. 

This proposed AD would also 

prohibit installing a pin P/N 369X1004– 

5 on any helicopter until the 

requirements of the AD have been 

accomplished. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 118 helicopters of U.S. 

Registry. 

We estimate that operators may incur 

the following costs in order to comply 

with this AD. Labor costs are estimated 

at $85 per hour. We estimate l/2 work 

hour to inspect and record any update 

for a total of $42.50 per helicopter and 

$5,015 for the U.S. fleet. If required, we 

estimate 1 work hour per helicopter to 

replace 10 pins because each blade has 

2 pins and each helicopter has 5 blades. 

Required parts are $445 for each pin. 

Based on these estimates, it would cost 

$4,535 per helicopter to replace 10 pins 

if the pins have exceeded their life limit. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed, I certify 

this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska to the extent that it justifies 

making a regulatory distinction; and 


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53030 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Proposed Rules 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by Reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

MD Helicopters Inc.: Docket No. FAA–2015– 

3659; Directorate Identifier 2014–SW– 

050–AD. 

(a) Applicability 

This AD applies to Model 369A, 

369D, 369E, 369FF, 369HE, 369HM, 

369HS, 500N, and 600N helicopters 

with an Aerometals main rotor blade 

attach pin (pin) part number (P/N) 

369X1004–5 installed, certificated in 

any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition 

as a pin remaining in service beyond its 

fatigue life. This condition could result 

in failure of a pin, loss of a main rotor 

blade, and subsequent loss of control of 

the helicopter. 

(c) Comments Due Date 

We must receive comments by 

November 2, 2015. 

(d) Compliance 

You are responsible for performing 

each action required by this AD within 

the specified compliance time unless it 

has already been accomplished prior to 

that time. 

(e) Required Actions 

(1) Within 100 hours time-in-service 

(TIS) or during the next annual 

inspection, whichever occurs first: 

(i) Review the maintenance records 

and determine the hours TIS of each pin 

P/N 369X1004–5 and whether there is a 

pin life limit listed in the Airworthiness 

Limitations Section of the applicable 

maintenance manual or Instructions for 

Continued Airworthiness (ICA). If the 

hours TIS on a pin is unknown, remove 

the pin from service. 

(ii) For Model 369A, 369HE, 369HM, 

and 369HS helicopters, if there is no pin 

life limit, establish a new life limit of 

5,760 hours TIS for each pin P/N 

369X1004–5 by making pen-and-ink 

changes or by inserting a copy of this 

AD into the Airworthiness Limitations 

Section of the maintenance manual or 

the ICA. Remove from service any pin 

that has 5,760 or more hours TIS. 

(iii) For Model 369D, 369E, 369FF, 

500N, and 600N helicopters, if there is 

no pin life limit, establish a new life 

limit of 7,600 hours TIS for each pin P/ 

N 369X1004–5 by making pen-and-ink 

changes or by inserting a copy of this 

AD into the Airworthiness Limitations 

Section of the maintenance manual or 

the ICA. Remove from service any pin 

that has 7,600 or more hours TIS. 

(iv) For all model helicopters, add the 

following statement to the 

Airworthiness Limitations Section of 

the maintenance manual or the ICA by 

making pen-and-ink changes or by 

inserting a copy of this AD: If 

interchanged between different model 

helicopters, the life limit of pin P/N 

369X1004–5 must be restricted to the 

lowest life limit indicated for the 

helicopter models and serial numbers 

affected. 

(2) Do not install a pin P/N 

369X1004–5 on any helicopter before 

the requirements of this AD have been 

accomplished. 

(f) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Los Angeles Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal 

to: Galib Abumeri, Aviation Safety 

Engineer, Transport Airplane 

Directorate, FAA, 3960 Paramount 

Blvd., Lakewood, California 90712; 

telephone (562) 627–5324 or email at 9- 

ANM-LAACO-AMOCREQUESTS@faa.gov. 

(2) For operations conducted under a 

14 CFR part 119 operating certificate or 

under 14 CFR part 91, subpart K, we 

suggest that you notify your principal 

inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office or certificate 

holding district office before operating 

any aircraft complying with this AD 

through an AMOC. 

(g) Additional Information 

Aerometals Service Bulletin Aero– 

SB–1103, dated July 2, 2014, and 

Aerometals Aero–ICA–101 

Supplemental Instructions for 

Continued Airworthiness, Revision NC, 

dated May 22, 2014, which are not 

incorporated by reference, contain 

additional information about the subject 

of this AD. For service information 

identified in this AD, contact 

Aerometals, 3920 Sandstone Dr., El 

Dorado Hills, CA 95762, telephone (916) 

939–6888, fax (916) 939–6555, 

www.aerometals.aero. You may review 

a copy of information at the FAA, Office 

of the Regional Counsel, Southwest 

Region, 10101 Hillwood Pkwy, Room 

6N–321, Fort Worth, TX 76177. 

(h) Subject 

Joint Aircraft Service Component 

(JASC) Code: 6210 Main Rotor Blades. 

Issued in Fort Worth, Texas, on August 21, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–21680 Filed 9–1–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3658; Directorate 

Identifier 2014–SW–039–AD] 

RIN 2120–AA64 

Airworthiness Directives; MD 

Helicopters Inc. (MDHI) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

MDHI Model 369A (Army OH–6A), 

369H, 369HE, 369HM, 369HS, 369D, 

369E, 369F, 369FF, and 500N 

helicopters. This proposed AD would 

require inspecting the auxiliary fuel 

pump (fuel pump) wire routing in the 

left-hand fuel cell and corrective action, 

if necessary. This proposed AD would 

also require installing a warning decal 

on the left-hand fuel cell access cover. 

This proposed AD is prompted by 

accidents resulting from incorrectly 

positioned fuel pump wiring within the 

fuel tank interfering with the operation 

of the fuel quantity sensor float, which 

caused an erroneous fuel quantity 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS